CN101981469A - Airborne electromagnetic transmitter coil system - Google Patents
Airborne electromagnetic transmitter coil system Download PDFInfo
- Publication number
- CN101981469A CN101981469A CN2009801066319A CN200980106631A CN101981469A CN 101981469 A CN101981469 A CN 101981469A CN 2009801066319 A CN2009801066319 A CN 2009801066319A CN 200980106631 A CN200980106631 A CN 200980106631A CN 101981469 A CN101981469 A CN 101981469A
- Authority
- CN
- China
- Prior art keywords
- framework
- transmitter coils
- assembly
- towing
- rope
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
- G01V3/15—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat
- G01V3/165—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat operating with magnetic or electric fields produced or modified by the object or by the detecting device
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
- G01V3/00—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation
- G01V3/15—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat
- G01V3/16—Electric or magnetic prospecting or detecting; Measuring magnetic field characteristics of the earth, e.g. declination, deviation specially adapted for use during transport, e.g. by a person, vehicle or boat specially adapted for use from aircraft
Landscapes
- Life Sciences & Earth Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Geophysics (AREA)
- Geology (AREA)
- Remote Sensing (AREA)
- General Life Sciences & Earth Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electromagnetism (AREA)
- Arrangements For Transmission Of Measured Signals (AREA)
- Near-Field Transmission Systems (AREA)
- Automobile Manufacture Line, Endless Track Vehicle, Trailer (AREA)
- Vehicle Body Suspensions (AREA)
- Details Of Aerials (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
A tow assembly for an airborne electromagnetic surveying system, comprising : a semi-rigid transmitter coil frame supporting a transmitter coil, the transmitter coil frame being formed from a plurality of serially connected frame sections forming a loop, the transmitter coil frame having articulating joints at a plurality of locations about a circumference thereof enabling the transmitter coil frame to at least partially bend at the articulating joints; and a suspension assembly for towing the transmitter coil frame behind an aircraft, the suspension assembly comprising a plurality of ropes and attached to the circumference of the transmitter coil frame at spaced apart locations.
Description
Technical field
The present invention relates generally to the transmitter coils system that is used in the aerial geology drawing field.
Background technology
The present known various electromagnetic techniques that have.Geophysical electromagnetism (" EM ") technology can be very effective when the conductivity of soil, rock and other conductive material of determining to reach deeply about 1 kilometer place.The distribution of conductivity that becomes with the degree of depth has very big meaning when alkalinous metal and uranium ore, aquifer and other tectonic structure are drawn.Initiatively the EM of geophysics method usually comprises: produce a magnetic field by near the transmitter coils system earth surface of being placed on is periodically applied electric current.This magnetic field induces electric current on the ground, measures the secondary magnetic field that is produced by these electric currents, thus the information that provides relevant ground conductivity to distribute.
The secondary magnetic field signal can use receiver coil system (it can measure three quadrature components of magnetic field to time-derivative dB/dt) or magnetometer (it measures magnetic field B) to measure.Then, the simulating signal that receives can be amplified by high-resolution high-speed AD converter (" ADC "), filtration and digitizing, and data store together with the locating information that obtains from GPS (" GPS ").Data Post can comprise the electrical model and the physical modelization on ground, to produce geophysical conductivity isogram.
EM measures and can carry out in frequency domain or time domain.In the electromagnetism (" FDEM ") of frequency domain was measured, transmitter coils generally sent fixing multiple frequency electromagnetic signal continuously, and receiver coil can be measured the signal as the function of time.The amount of recording can comprise signal amplitude and phase place, or of equal value saying, promptly as the homophase of frequency function with the amplitude of quadrature.
In electromagnetism (" the TDEM ") system of time domain, current impulse can be applied to transmitter coils during connecting, and produces EM magnetic field once or that send, then, disconnects magnetic field at off period.Secondary singal can be measured as the function of time at the receiver coil place.The model of the conductivity of geology object and geometrical property is combined on the delay of off period signal amplitude and ground, can be used to produce the isogram of conductivity like this.United States Patent (USP) 7,157,914 show the example of a TDEM system.
The EM method can comprise the aerial applications based on the application on ground and use aircraft and helicopter.Aerial method can be very convenient for the prospecting in big zone, and be used for exploring ore body, geology drawing, water geology and the environmental inspection of the conduction in the sill that is embedded in drag.By means of unrestriced example, in some aerial electromagnetism (" AEM ") system, at aircraft or helicopter (for example with almost constant speed, respectively up to 75m/s or 30m/s) (for example sow discord along parallel equidistant almost apart from straight line, 50m to 200m) side (for example approaches on the constant height on the ground, be about 120m or 30m respectively) when flying, can obtain data.Measurement can be carried out at regular intervals, for example, and in the scope of 1m to 100m.
When time domain electromagnetism (" the HTEM ") system of design and installation on helicopter, have the feature of a plurality of requirements, it comprises: high signal is led resolution to noise than (" SNR "), high electricity, and high spatial resolution (side direction and the degree of depth to).By reducing the signal in system noise or the raising receiver coil, can realize that high signal is to the noise ratio.One of method that improves signal means can be to increase a magnetic field.
For the point away from transmitter coils, the magnetic field size is proportional to the magnetic dipole moment of coil, and be inversely proportional to off-line circle distance cube.The magnetic dipole moment of coil is long-pending N*I*A, and wherein, N is the number of turn, and I is an electric current, and A is an area coil.The induction coefficient of coil is proportional to N
2* D, wherein, N is the number of turn, D is a coil diameter.Provide by following formula at the voltage that the receiver coil internal induction goes out by magnetic field B: N*A*dB/dt, wherein, coil sensitivity is that N * A is the product of turn number N and area coil A, and dB/dt is the derivative of magnetic field to the time.
No matter when reconnoitring target is the conductivity of describing nearly surface, and the little magnetic dipole moment that then has quick disconnection can be suitable, and in this case, the number of turn in the transmitter coils is less usually, therefore, draws the magnetic dipole moment and the induction coefficient that reduce.On the contrary,, can require long trip time, the more important thing is, improve the magnetic dipole moment of transmitter coils for the conductor of surveying big degree of depth place.
No matter when can guarantee the increase of magnetic dipole moment, then just be necessary to increase electric current I, number of turn N or transmitter coils area A.Can be subjected to the restriction of helicopter generator from the power supply of single-engined helicopter, unless use accessory power supply.In addition, the limiting factor for the magnitude of current in the transmitter coils is the resistance of coil and trailing cable.For the cable of regular length, square multiply by resistance (P=I*I*R) from what the consumption of the power P of helicopter power supply was approximately equal to electric current.Reducing resistance and will increase electric current, is the square root of decrease.The available heavy pound lead that reduces of resistance is realized in the ring, but its weight correspondingly increases, and multiply by resistivity divided by the conductive wire cross-section area because resistance is proportional to length approx.The weight of transmitter coils also is proportional to the length of cable, and therefore, it is proportional to the square root of number of turn N or transmitter coils area A.Because the weight of transmitter coils increases with number of turn N linearly with the quadratic sum of electric current I, and increase with the square root of area A, for the given towing weight ability of helicopter, a kind of mode that increases the magnetic dipole moment of transmitter coils can be to increase area A.When the I, the N that optimize transmitter coils and A, another factor that will consider is the short trip time that needs in the time domain measurement, and this can require the low induction coefficient of transmitter coils, and induction coefficient is proportional to the square root of the quadratic sum transmitter coils area of N.
Yet, increase the transmitter coils diameter and can reduce air dynamic behaviour and increase drag force.Large scale structure take off and the landing process in can be subjected to stress, therefore,, usually have a restriction for the size deployable and rigid structure that do not disconnect.Strengthen this structure make its take off and the landing process in do not rupture, may mean that the weight of structure will increase.In addition, keeping the shape of transmitter coils in flight course, can be very important for fixing magnetic dipole moment is provided, so that it is bad to measure mass conservation.Therefore, require to increase magnetic dipole moment and can need the many factors of balance carefully.
Summary of the invention
According to an example embodiment, a kind of towing assembly that is used for aerial electromagnetism survey system, it comprises: the semirigid transmitter coils framework of supporting transmitter coils, the transmitter coils framework is formed by a plurality of frame parts that are connected in series that form a ring, the transmitter coils framework has at a plurality of positions around the hinged joint of its circumference, can make the transmitter coils framework crooked at least in part at pin joint; And the mounting assembly that pulls the transmitter coils framework in the aircraft back, this mounting assembly comprises a plurality of ropes, and is attached on the transmitter coils framework circumference at spaced position.
According to another example embodiment, a kind of method that is provided for the towing assembly of aerial electromagnetism survey system, it comprises: transmitter coils is provided; A plurality of tubular frame members are provided; A plurality of tubular frame members are connected in series into a ring, and the transmitter coils framework of formation supporting transmitter coils, joint between at least some tubular frame members allows to rotate, and this makes the transmitter coils framework crooked at least in part in response to acting on power on the transmitter coils scaffold; Mounting assembly is provided, and this mounting assembly is at helicopter back towing transmitter coils scaffold, and a plurality of positions around the transmitter coils framework connect mounting assembly.
In one aspect of the invention, a kind of aerial time domain electromagnetism survey system is disclosed, it comprises: be connected to the towing assembly on the aircraft, this towing assembly comprises: scaffold, scaffold comprises transmitter part and receiver part, the transceiver portion branch comprises sender device, and the transceiver portion branch comprises the supporting structure that is generally semi-rigid module that is used to support sender device; Receiver partly comprises receiver scaffold and sensor device.
According to a further aspect in the invention, disclose a kind of aerial time domain electromagnetism prospecting transmitter coils, it comprises: the transmitter part, and it comprises: transmitter coils; And semi-rigid module support structure; Wherein, semi-rigid module support structure supporting transmitter coils; And the towing assembly that comprises scaffold that is connected to aircraft; And wherein, transmitter partly is included in the scaffold; And wherein, supporting frame structure can make scaffold be positioned at substantially horizontal position awing, and increases magnetic dipole moment.
Also have on the other hand of the present invention, disclose a kind of electromagnetism that is used to suspend and reconnoitred the netted device that suspends of transmitter coils, it comprises: have the net that suspends that cart rope connects, it operationally is attached on the aircraft, the netting gear that suspends has a plurality of ropes, and rope is attached to semi-rigid module support structure by means of a plurality of attachment point between a plurality of ropes; And the transmitter coils that is used to obtain to reconnoitre data, it is online that transmitter coils is attached to suspending of towing rope junction; Wherein, the distance definition between attachment point and the rope length becomes to provide the substantially horizontal location of transmitter coils awing; And wherein, semi-rigid modular structure comprises the transmitter scaffold, and it supports transmitter coils, and has the transmitter scaffold part of a plurality of interconnection, so that each transmitter scaffold part can be rotated around its axis with respect to contiguous part.
Aspect this, before in detail explaining at least one embodiment of the present invention, should be understood that, the present invention be not limited to its to set forth in the application of CONSTRUCTED SPECIFICATION and the following detailed description or accompanying drawing shown in the layout of parts.The present invention can have other embodiment, can put into practice in every way and implement.Also have, should be understood that word used herein and term only are for purpose of description, should not see as is restriction.
Description of drawings
Fig. 1 is the top perspective view of the towing assembly that comprises transmitter coils framework and receiver coil framework of one example embodiment according to the present invention.
Figure 1A is the enlarged drawing of the part 1A of Fig. 1, is shown specifically the receiver coil framework.
Fig. 2 is a planimetric map, and the side that Fig. 1 pulls the transmitter coils framework of assembly is shown.
Fig. 3 is the planimetric map of the parts of transmitter coils framework one side.
Fig. 4 is with the transmitter coils framework in the air position of prospecting speed flight and the stereographic map of receiver coil framework.
Fig. 5 is with the transmitter coils framework in the air position of prospecting speed flight and the side view of receiver coil framework.
Fig. 6 just takes off before back or the landing with low speed or does not have transmitter coils framework in the air position of horizontal speed flight and the side view of receiver coil framework.
Fig. 7 be when a framework part contacts with ground, taking off or the landing process in position in midair in the transmitter coils framework and the side view of receiver coil framework.
Fig. 8 A and 8B are respectively upward view and side view, illustrate to be used for the netted support of suspending of transmitter coils framework according to another example embodiment.
Fig. 9 is a top perspective view, and another example of the towing assembly of another example embodiment according to the present invention is shown.
In the accompanying drawings, embodiments of the invention illustrate by means of example.On expressing, be appreciated that the description of this paper and accompanying drawing only are the purposes that is used for explanation, and aid in understanding, be not intended to limit limitation of the present invention.
Embodiment
The embodiment of example of the present invention relates to the big transmitter coils that can be launched by aircraft, and aircraft is such as, but not limited to single-engined helicopter, and it can be used for the time domain electromagnetic system such as aerial HTEM survey system.In electromagnetism survey system field, need a kind of transmitter coils that has such as size scalability feature, and the transmitter coils supporting structure that can repair at the scene.In some example embodiment at least, the towing assembly has the transmitter coils supporting structure, and this structure is semirigid structure, when structure reduces the probability that destroys from the aircraft Shi Qike that flies out, and described aircraft such as the helicopter of puffer cheaply.In addition, the transmitter coils supporting structure can be formed by a plurality of parts, and thus, it can repair and allow the physical dimension upgrading at the scene.
The present invention's aerotow component system of some example embodiment and device at least can be used for exploring alkalinous metal and uranium ore under the certain depth, for example degree of depth in 1 kilometer range, and other the degree of depth.In some example embodiment, the towing assembly can have one or more following features: it can comprise the transmitter coils with big magnetic dipole moment; It can provide flight stability; It can very light in weight and is therefore compatible with flivver, such as single-engined helicopter; It can easily transport, easily erects at the scene and repair.The transmitter coils framework of the embodiment of example can comprise semirigid modular structure according to the present invention, its can take off or land during reduce to damage or the probability of fracture.
In addition, the embodiment of some example can comprise big transmitter coils, and it can be launched by flivver, and such as single-engined helicopter, it provides high signal to the receiver coil of noise than (" SNR ").
In one embodiment, the transmitter coils framework comprises the semi-rigid modular structure of being made up of the polygon pipe of the electrical isolation with self-lubricating joint, and the rope suspension system.Receiver coil can middle heart be attached in the transmitter coils framework, and this transmitter coils framework has independent netted rope suspension system.
Different embodiments of the invention can have the framed structure of the variation that comprises the certain limit structure, location, size, material and the weight of coil.
Fig. 1 and 4 illustrates the towing assembly that is used for aerial electromagnetism prospecting of the embodiment of the example according to the present invention.As shown in figs. 1 and 4, the towing assembly comprises the polygonal transmitter coils framework 10 that is built up by a plurality of pipes 18, and such as dodecagon, pipe 18 is by glass fibre, Kevlar or other suitable lightweight and durable material structure that can electrical isolation.Polygonal receiver coil framework 12 for example can be octagonal shape, and receiver coil framework 12 is positioned at the center of transmitter coils framework 10.The rope of two framework available radial is 14 to couple together.In the embodiment shown, rope 14 extends under tension force radially outwardly, extends to the relevant position from public center hub 9, and these positions are spaced equably around the periphery or the circumference of transmitter coils framework 10.Receiver coil framework 12 is attached to rope 14 and is supported by rope, and receiver coil framework 12 is concentric with transmitter coils framework 10.United States Patent (USP) 7,157,914 (this paper is to introduce its content referring to mode) have been described a suitable example, this case introduction rope system radially how can be used to connect transmitter coils framework and supporting receiver coil framework.
Two magazines 10,12 can suspend in the nigh horizontal level by suspension system 11, and suspension system 11 is attached to polygonal transmitter coils framework 10.The suspension system 11 that is connected to transmitter coils framework 10 comprises the cable 15 that suspends of cart rope annex, and it is attachable on the aircraft, and purpose is with the transmitter coils framework 10 skyborne position that suspends.The lower end of the cable 15 that suspends of cart rope annex is connected to supporting rope assembly 13, and this assembly is connected to a plurality of pickup points around the circumference of transmitter coils framework 10 again.
In the embodiment shown in Fig. 1 and 4, supporting rope assembly 13 comprises many ropes 16, and they respectively have the lower end that is attached to the corresponding pickup point on transmitter coils framework 10 circumferences, and the upper end of lower end that is attached to the cable 15 that suspends of cart rope annex.In some example embodiment at least, rope 16 respectively is attached to the corresponding bight of transmitter coils framework.United States Patent (USP) 7,157,914 (this paper is to introduce its content referring to mode) have been described a suitable example of supporting rope assembly 13, and this supporting rope assembly 13 can be used to support transmitter coils framework 10.In the embodiment of another example, the supporting rope assembly of suspension system 11 can be configured to by a plurality of ropes, all ropes form taper net or the reticulate texture shown in Fig. 8 A and 8B, and as submitted on Dec 14th, 2006 and with the U.S. Patent application 11/610,556 that US2008/0143130 publishes (this paper is to introduce its content referring to mode) described.Other structure of suspension system also is possible.
Fig. 2 illustrates the example of a side 18 of transmitter coils framework 10, and Fig. 3 illustrates all parts of this side 18.Shown in Fig. 2 and 3, in one embodiment, each polygon side 18 can comprise the tubular frame part 20 of straight line and the tubular frame part 22 of elbow. Tubular frame part 20 and 22 is connected in series together and forms closed ring.Sweep 21 or elbow in the side 18 can be centrally located in the tubular elbow part 22.In the embodiment shown, side 18 comprises three straight line barrel portions 20 that are connected in series, and connects elbow barrel portion 22 behind the straight line barrel portion.Use a plurality of straight line barrel portions that a side 18 is provided, can be by adding the size that the straight line barrel portion amplifies transmitter coils framework 10 to side, or by from side, removing the size that the straight line barrel portion reduces transmitter coils framework 10.
In the embodiment shown in fig. 3, it is the terminal conduit 24 that 26 sun inserts that each barrel portion 20 and 22 has the overall diameter that stretches out from an end, and the other end is cloudy socket 25, and like this, part 20,22 mode that can end-to-endly be complementary assembles and forms the transmitter coils framework.Outstanding insertion terminal conduit 24 can be made of carbon fiber, lubricated glass fibre or any other material, and it allows each barrel portion 20,22 to be connected to the cloudy socket end 25 of neighbouring part with rotating manner.When transmitter coils framework 10 structures were assembled, each barrel portion can rotate around the axis along polygon side 18 with respect to its contiguous barrel portion.In order to provide or to improve lubricity, outstanding insertion terminal conduit 24 can be lubricated with the lubricant of carbon or the splash of molybdenum base, or with reaching any other lubricant that requirement is rotated.In some example embodiment, some barrel portion can have two cloudy socket end, alternates with the barrel portion with two positive insertion ends.
In example embodiment, transmitter coils framework 10 forms continuous transmitter coils passage, and it can hold transmitter coils (dotted line 7 illustrates among Fig. 2).In some example embodiment at least, transmitter coils 7 by be placed on barrel portion 20 and 22 in a circle or multiturn (for example, four circles) heavy pound aluminum conductor forms, and be connected to power supply on the aircraft 28 with heavy pound copper cable, hanging transmitter coils framework 10 in the air position such as the aircraft of helicopter.In some example embodiment at least of transmitter coils framework 10, the aluminium cable can draw the such light structure of conductive material that substitutes of ratio such as copper under same current capacity.In certain embodiments, the general assembly (TW) of towing component system is little of allowing to be pulled it, the small-sized single-engined helicopter of such aircraft such as low operating cost by aircraft 28.
In non-limiting example embodiment of the present invention, transmitter coils 7 can have and for example is the maximum current capacity of 250A, and the load cycle rate is up to 50%.The magnetic dipole moment value of transmitter coils for example can be 500,000A.m
2, inductance value for example is 1.5mH.The sensitivity N*A of receiver coil for example is 500m
2, wherein, N is the number of turn of coil, and A is an area coil.
Should be realized that the present magnetic dipole moment of transmitter coils 7 and further feature can change adapting to external parameter, the peak power that can supply such as tug plane.
Figure 4 and 5 respectively illustrate main transmitter coils framework 10 and the receiver coil framework 12 that the prospecting purpose is located in-flight.
As shown in Figure 5, in some example embodiment at least, supporting rope assembly 13 is configured to: when flying aloft with prospecting speed, main transmitter coils framework 10 and receiver coil framework 12 are positioned at substantially horizontal position, so that suspension system 11 supporting transmitter coils 7 and receiver coils 5 make corresponding dipole axis approximate vertical.Each length that suspends cable or rope 16 can be like this: when at flight aerial, transmitter coils framework 10 and receiver coil framework can be positioned at the position of approximate horizontal, make suspension point be positioned at a certain angle from perpendicular line.In order to reach this position, long cable or rope 30 can be positioned on the rear side or the tail side of supporting rope assembly 13, and supporting rope assembly 13 front sides that short cable or rope 32 can be positioned at suspension system 11 or lead side.
In some embodiment at least, multiple spot suspension system 11 can help to realize the stability of the desirable flight position of supporting that improves.Specifically, multiple spot suspension system configuration 11 can produce a pulling force, and this pulling force makes transmitter coils framework 10 remain on the position of approximate horizontal.Although the state of suspending can produce total little drag force, the longer rope 30 that is positioned at rear side can produce than the shorter rope 32 remarkable big drag forces that are positioned at the front side.This can keep transmitter coils framework 10 in place, and prevents that it from centering on its vertical axis and rotating.As shown in Figure 4, also can on rear side that pulls modular construction or tail side, a little dynamic (dynamical) fin 19 of stable air be set, in the turning between the prospecting circuit, to provide additional stability.
In certain embodiments, transmitter coils framework 10 can have sizable diameter, and for example, overall dimensions can measure greater than 25m.In certain embodiments, disclosed physical construction can help the vibration that wind brings out is reduced to minimum, and in flight course, helping to keep the shape of transmitter coils, it can allow the magnetic dipole moment of safeguarding stability, and can be used to improve the signal to noise ratio (S/N ratio) at receiver coil place.
In the above embodiments of the present invention, transmitter coils framework 10 is structures that the polygon of hinged tubular segment is fixed together, in flight course by combined suspension system 11 with optimize transmitter coils cable weight and keep stability.The towing modular construction can be designed to enough weight, when wind-engaging impacts in flight course, can upwards not overturn, but sufficiently gently can be pulled such as the such aircraft 28 of single-engined helicopter again.For instance, towing assembly weight is about 500kg.In addition, tubular- shaped structures 20 and 22 can have enough rigidity, so that structure can not disconnect, and acts on this structural power can bear the force of compression of suspension system 11 and aircraft 28 flights the time.By means of non-limiting instance, flying speed for example can be 25m/s to 50m/s.
Fig. 6 illustrates the towing assembly and transmitter coils framework 10 and receiver coil framework 12 when not being flatly mobile such as the such aircraft 28 of helicopter.This location can take off and the landing process in take place.In these cases, the central axis of transmitter coils framework 10 can be out-of-level, and can be with perpendicular line at an angle.In the landing operating process, when transmitter coils touched ground, the barrel portion 20 of transmitter coils framework 10 and 22 can relative to each other rotate.In this regard, Fig. 7 further illustrates how towing modular construction side 18 can adjust transmitter coils framework 10 by the framework of articulated joint place between the barrel portion 20,22 of crooked transmitter coils framework 10 in the landing process shape." folding " ability of transmitter coils scaffold can have makes the structure upper stress reduce to minimum effect.
In some was used at least, the semi-rigid transmitter coils framework 10 of modularization had many benefits for the rigid mechanical structure.For example, traditional large-scale rigid frame can form mechanical stress, and mechanical stress causes rupturing in the landing process.Adopted and behind the semirigid structure of its lubrication connection rotation, just can reduce structural stress, and can improve the probability of smooth landing.Semi-rigid modular structure also can make transmitter coils drop on the irregular landform.When prospecting high mountain or rugged landform, there helicopter and landing area may be located less than on the level land, and aforementioned capabilities is exactly a kind of very important consideration so.
In some example embodiment, transmitter coils framework 10 and receiver coil framework 12 can be configured to sizable size, and overall dimension is measured and is approximately 25m or bigger.The flexibility of semirigid structure, its polygonal shape and at the size of can selecteed individual part determining, make the towing assembly can be disassembled and can be contained in transportation in the TEU (Twenty-foot Equivalent Unit), the two combination can help to construct the system with the very big coil that can assemble at the scene, and helps to take off and not recurring structure fracture when landing.
In example embodiment, modular transmitter coils framed structure can disassemble.Each side 18 can be made up of the part 20 and 22 of certain-length and width, such length and width allow carrying or transportation, for example adopt the air transport of standard and need not particular processing, like this, the parts of transmitter coils framework 10 can be contained in transportation in the container, such as the Air Container of standard, and can assemble at the scene.If transmitter coils framework 10 is damaged, then can repair by the parts of more changing damage at the scene.
Those skilled in the art will recognize that, also can put into practice other variant to embodiment as herein described, and can not depart from the scope of the present invention.Therefore, other modification is possible.For example, structure can be amplified in proportion and be produced big magnetic dipole moment, with use helicopter to carry out special prospecting to require consistently, make the towing ability realize surveying the conductivity that requires ground, degree of depth place greater than single-engined helicopter.In addition, the transmitter coils structure can be made of various materials, perhaps can allow suspension system that pulling strengrth, lubricated rotational characteristic and above-mentioned lightweight structure are arranged.In addition, structure also can be applicable to the electromagnetism survey system of frequency domain.In certain embodiments, receiver coil or sensor can be positioned at outside the transmitter coils frame center the somewhere-for example, it can pull in transmitter coils framework back, or be positioned at the circumference of transmitter coils framework prejudicially.
In addition, transmitter coils framework 10 can be formed by a plurality of barrel portions, and barrel portion is curved, makes framework 10 be circular rather than approaching circular polygon.
Fig. 9 illustrates the towing assembly 100 of another example embodiment according to the present invention.This towing assembly 100 is similar to above referring to figs. 1 through the described towing assembly of 8b, the exception part is, towing assembly 100 also comprises the tubular compensating coil framework 117 that supports compensating coil 119, so that compensate for the effect in a magnetic field that is produced by transmitter coils 7 near receiver coil 5.In an example embodiment, compensating coil framework 117 is equal to transmitter coils framework 10 in structure and mechanically actuated, but smaller.Therefore, compensating coil framework 117 is also formed by a plurality of frame parts that are connected in series that form a ring, and has hinged joint around the circumference of framework at a plurality of positions, can make the compensating coil framework crooked at least in part in articulated joint place.In example embodiment, compensating coil is by 113 supportings of supporting rope assembly, this supporting rope assembly 113 comprises a plurality of ropes 127, and their lower end respectively is attached to the corresponding pickup point on compensating coil framework 117 circumferences, and their upper end is attached to the lower end of the cable 15 that suspends of cart rope annex.In some example embodiment, compensating coil supporting rope 127 is attached to than transmitter coils and supports on the trailing cable 15 of rope 16 more following positions.Compensating coil framework 117 for example can be about transmitter coils framework 10 diameter 1/4, and also can be connected on the corresponding bight on the rope 14 that radially extends, so that compensating coil 119 keeps aliging with transmitter coils 7 and receiver coil 5 substantially concentricly.Be similar to the net that suspends shown in Fig. 8 A and the 8B and alternately be used for supporting the compensating coil framework.
Claims (19)
1. towing assembly that is used for aerial electromagnetism survey system comprises:
The semirigid transmitter coils framework of supporting transmitter coils, described transmitter coils framework is formed by a plurality of frame parts that are connected in series that form a ring, described transmitter coils framework has at a plurality of positions around the hinged joint of its circumference, can make described transmitter coils framework crooked at least in part in articulated joint place; And
Pull the mounting assembly of described transmitter coils framework in the aircraft back, described mounting assembly comprises a plurality of ropes, and is attached at spaced position on the circumference of described transmitter coils framework.
2. towing assembly as claimed in claim 1 is characterized in that, described towing assembly comprises: a plurality of connection ropes, each connects the corresponding site on rope extends outwardly into described transmitter coils framework from public hub the circumference.
3. towing assembly as claimed in claim 2 is characterized in that, comprises the receiver coil framework that supports receiver coil, and described receiver coil framework is supported by a plurality of connection ropes, makes described receiver coil concentric with described transmitter coils basically.
4. as any one described towing assembly in the claim 1 to 3, it is characterized in that, described mounting assembly is led the vertical height of the vertical height of side less than its tail side at it, with the flying speed that requires described transmitter coils framework is bearing in the position of approximate horizontal thus.
5. as any one described towing assembly in the claim 1 to 4, it is characterized in that, the rope of described towing assembly comprises cart rope and a plurality of rope that suspends that is attached on the aircraft, and the described rope that suspends respectively has the upper end that is attached to described cart rope one end and is connected to around the lower end of the corresponding site at the spaced position of the circumference of described towing component framework.
6. towing assembly as claimed in claim 5 is characterized in that, the length that is attached to the rope that suspends on the afterbody of described transmitter coils framework is longer than the length of leading the rope that suspends in the portion that is attached to described transmitter coils framework.
7. as any one described towing assembly in the claim 1 to 4, it is characterized in that, the rope of described mounting assembly comprises cart rope that is attached on the aircraft and a plurality of ropes that form web frame, first end of described web frame is attached to an end of described cart rope, and second end of described web frame is attached to around the spaced position of the circumference of described towing component framework.
8. as any one described towing assembly in the claim 1 to 7, it is characterized in that the articulated joint of described transmitter coils framework is the articulated joint between at least some frame parts that are connected in series.
9. towing assembly as claimed in claim 8 is characterized in that, the articulated joint between at least some frame parts that are connected in series is lubricated.
10. pull assembly as claimed in claim 8 or 9, it is characterized in that, each male portion by a part in the described transmitter frame part of described articulated joint forms, and described male portion is received within the corresponding female part of another part in the described transmitter frame part.
11. as any one described towing assembly in the claim 1 to 10, it is characterized in that described frame part is a barrel portion, described barrel portion joins together to form continuous interior loop passage, described transmitter coils is received within the described passage.
12. towing assembly as claimed in claim 11 is characterized in that, described barrel portion comprises straight line barrel portion and elbow barrel portion.
13. towing assembly as claimed in claim 12 is characterized in that, described transmitter coils scaffold has a plurality of sides, and described a plurality of sides join together to form polygonal shape.
14. towing assembly as claimed in claim 12 is characterized in that the barrel portion of a plurality of straight lines is included in each side.
15. as any one described towing assembly in the claim 1 to 14, it is characterized in that, comprising:
The semi-rigid compensating coil framework of supporting compensating coil, described compensating coil framework is formed by a plurality of barrel portions that are connected in series, thereby form a ring, described compensating coil framework has articulated joint at a plurality of positions around its circumference, can make described compensating coil framework crooked at least in part in articulated joint place; And
The compensating coil mounting assembly is used for suspending and to pull described compensating coil framework in place with respect to described transmitter coils framework, and described compensating coil mounting assembly comprises a plurality of ropes and is attached at spaced position on the circumference of described compensating coil framework.
16. a method that is provided for the towing assembly of aerial electromagnetism survey system comprises:
Transmitter coils is provided;
A plurality of tubular frame members are provided;
Described a plurality of tubular frame members are connected in series into a ring, and the transmitter coils framework of the described transmitter coils of formation supporting, joint between at least some tubular frame members allows to rotate, and this makes described transmitter coils framework crooked at least in part in response to acting on power on the described transmitter coils scaffold;
Mounting assembly is provided, and described mounting assembly pulls described transmitter coils scaffold in the helicopter back, and a plurality of positions around described transmitter coils framework connect described mounting assembly.
17. method as claimed in claim 16 is characterized in that, described transmitter coils scaffold has the dodecagonal shape.
18., it is characterized in that, connect described mounting assembly, thereby when flying, described transmitter coils framework is bearing in the substantial horizontal orientation with observation flight speed as claim 16 or 17 described methods.
19. an aerial time domain electromagnetism survey system comprises:
(a) be used to be connected to towing assembly on the aircraft, described towing assembly comprises:
(i) scaffold, described scaffold comprises:
(A) comprise the transmitter part of sender device, described transceiver portion branch comprises roughly semi-rigid module support structure, described module support structure comprises a plurality of framing components that are connected in series, be used for supporting described sender device, described framing component is arranged to and can be rotated with respect to contiguous framing component; And
(B) receiver part, described receiver partly comprises receiver scaffold and sensor device.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/036,657 | 2008-02-25 | ||
| US12/036,657 US7948237B2 (en) | 2008-02-25 | 2008-02-25 | Large airborne time-domain electromagnetic transmitter coil system and apparatus |
| PCT/CA2009/000217 WO2009105873A1 (en) | 2008-02-25 | 2009-02-25 | Airborne electromagnetic transmitter coil system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101981469A true CN101981469A (en) | 2011-02-23 |
| CN101981469B CN101981469B (en) | 2014-04-16 |
Family
ID=40997652
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200980106631.9A Active CN101981469B (en) | 2008-02-25 | 2009-02-25 | Airborne electromagnetic transmitter coil system |
Country Status (10)
| Country | Link |
|---|---|
| US (2) | US7948237B2 (en) |
| EP (1) | EP2247966B1 (en) |
| CN (1) | CN101981469B (en) |
| AU (1) | AU2009219062B2 (en) |
| BR (1) | BRPI0906004A8 (en) |
| CA (1) | CA2702346C (en) |
| DK (1) | DK2247966T3 (en) |
| RU (1) | RU2494420C2 (en) |
| WO (1) | WO2009105873A1 (en) |
| ZA (1) | ZA201005931B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443415A (en) * | 2014-11-27 | 2015-03-25 | 湖南航天机电设备与特种材料研究所 | Carrying structure for aviation transient electromagnetic coil |
| CN105083554A (en) * | 2014-05-14 | 2015-11-25 | 空客直升机德国有限公司 | External load mass rope of a rotorcraft |
| CN105824049A (en) * | 2016-03-21 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Hanging-type helicopter time domain aeromagnetic detection pod |
| CN106164706A (en) * | 2014-02-28 | 2016-11-23 | 艾克讯通讯有限公司 | The airborne platform including attitude updating device and the towing hitch assembly being associated for aircraft |
| CN106199741A (en) * | 2016-07-04 | 2016-12-07 | 哈尔滨工业大学 | A kind of pod propulsion time domain aviation transient electromagnetic exploration system based on lightweight gas tube supporting construction |
| CN106226820A (en) * | 2016-07-04 | 2016-12-14 | 哈尔滨工业大学 | A kind of lightweight inflation ring supporting construction for pod propulsion time domain aviation transient electromagnetic exploration system |
| CN107102369A (en) * | 2017-06-05 | 2017-08-29 | 吉林大学 | Airborne low-temperature superconducting nuclear magnetic resonance shallow-layer oil seepage detection device and detection method |
| CN112068211A (en) * | 2020-07-30 | 2020-12-11 | 成都理工大学 | Half time domain electromagnetic prospecting system of aviation of unmanned aerial vehicle |
Families Citing this family (39)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8674701B2 (en) * | 2008-02-25 | 2014-03-18 | Geotech Airborne Limited | Airborne electromagnetic transmitter coil system |
| CN102770784B (en) | 2009-10-23 | 2016-06-08 | 吉欧泰科航空物探有限公司 | The towing assembly of geophysical exploration is carried out for Fixed Wing AirVehicle |
| CA2829285A1 (en) * | 2011-03-07 | 2012-09-13 | Geotech Airborne Limited | Monitoring the dipole moment vector of an airborne electromagnetic survey system |
| CA2840545C (en) | 2011-06-29 | 2017-06-13 | Minesense Technologies Ltd. | Extracting mined ore, minerals or other materials using sensor-based sorting |
| US9316537B2 (en) | 2011-06-29 | 2016-04-19 | Minesense Technologies Ltd. | Sorting materials using a pattern recognition, such as upgrading nickel laterite ores through electromagnetic sensor-based methods |
| US11219927B2 (en) | 2011-06-29 | 2022-01-11 | Minesense Technologies Ltd. | Sorting materials using pattern recognition, such as upgrading nickel laterite ores through electromagnetic sensor-based methods |
| AU2012334757B2 (en) * | 2011-11-08 | 2016-05-19 | Cgg Data Services Ag | Airborne electromagnetic system with rigid loop structure comprised of lightweight modular non-rotational frames |
| EP3369488B1 (en) | 2012-05-01 | 2021-06-23 | Minesense Technologies Ltd. | High capacity cascade-type mineral sorting method |
| US9817147B2 (en) * | 2012-08-17 | 2017-11-14 | Cgg Data Services Ag | Airborne electromagnetic system with large suspension coil assembly |
| CA2883011C (en) * | 2013-04-15 | 2021-01-19 | Nrg Exploration Cc | Transmitter coil system for airborne surveys |
| CA2916738A1 (en) * | 2013-07-05 | 2015-01-08 | Outer-Rim Developments Pty Ltd | A support structure |
| US10018745B2 (en) | 2013-12-11 | 2018-07-10 | Geotech Ltd. | Monitoring the dipole moment vector of an airborne electromagnetic survey system |
| US9612354B2 (en) | 2014-02-06 | 2017-04-04 | Cgg Services Sas | Geophysical survey system using hybrid aircraft |
| DK178046B1 (en) | 2014-02-28 | 2015-04-13 | Selskabet Af 6 April 2010 Aps | Airborne Electromagnetic Survey System with Aerodynamic Frame Segments; and Methods of Surveying using Such |
| AU2015201655B2 (en) | 2014-04-07 | 2020-01-02 | Xcalibur Mph Switzerland Sa | Electromagnetic receiver tracking and real-time calibration system and method |
| RU2557354C1 (en) * | 2014-04-17 | 2015-07-20 | Федеральное Государственное Унитарное Предприятие "Сибирский Научно-Исследовательский Институт Геологии, Геофизики И Минерального Сырья" | Apparatus and method for aerophysical survey |
| WO2015173642A1 (en) * | 2014-05-12 | 2015-11-19 | Cgg Services Sa | Low-frequency receiver coil suspension system |
| CN112536242B (en) | 2014-07-21 | 2023-08-04 | 感矿科技有限公司 | High capacity separation of coarse ore minerals from waste minerals |
| WO2016011551A1 (en) | 2014-07-21 | 2016-01-28 | Minesense Technologies Ltd. | High capacity separation of coarse ore minerals from waste minerals |
| AU2015207977B2 (en) | 2014-08-06 | 2021-01-21 | Xcalibur Mph Switzerland Sa | Systems and methods for active cancellation of transient signals and dynamic loop configuration |
| US9921331B2 (en) | 2014-12-17 | 2018-03-20 | Cgg Services Sas | Multi-sensor system for airborne geophysical prospecting and method |
| WO2016134483A1 (en) * | 2015-02-27 | 2016-09-01 | Geotech Ltd. | Electromagnetic survey system having tow assembly with attitude adjustment |
| US10472065B2 (en) * | 2015-05-12 | 2019-11-12 | Quanta Associates, L.P. | Hovering aircraft belly bar clasp |
| US10507920B2 (en) * | 2015-05-18 | 2019-12-17 | Sikorsky Aircraft Corp. | Systems and methods for lifting body vibration control |
| RU2629705C1 (en) * | 2016-04-19 | 2017-08-31 | Закрытое акционерное общество "Аэрогеофизическая разведка" | Method of high-precise electromagnetic sensings and device for its implementation |
| US10920585B2 (en) | 2017-12-26 | 2021-02-16 | Saudi Arabian Oil Company | Determining sand-dune velocity variations |
| US10870558B2 (en) | 2018-02-08 | 2020-12-22 | Vita Inclinata Technologies, Inc. | Integrated suspended load control apparatuses, systems, and methods |
| US11945697B2 (en) | 2018-02-08 | 2024-04-02 | Vita Inclinata Ip Holdings Llc | Multiple remote control for suspended load control equipment apparatus, system, and method |
| US11209836B1 (en) | 2018-02-08 | 2021-12-28 | Vita Inclinata Technologies, Inc. | Long line loiter apparatus, system, and method |
| RU195445U1 (en) * | 2018-02-08 | 2020-01-28 | Вита Инклината Текнолоджис, Инк. | EXTERNAL SUSPENSION LOAD STABILITY DEVICE |
| US11142316B2 (en) | 2018-02-08 | 2021-10-12 | Vita Inclinata Technologies, Inc. | Control of drone-load system method, system, and apparatus |
| US11142433B2 (en) | 2018-02-08 | 2021-10-12 | Vita Inclinata Technologies, Inc. | Bidirectional thrust apparatus, system, and method |
| CN109799540B (en) * | 2018-12-25 | 2020-12-11 | 核工业北京地质研究院 | Volcanic rock type uranium deposit magnetic susceptibility inversion method based on geological information constraint |
| US11746951B2 (en) | 2019-02-26 | 2023-09-05 | Vita Inclinata Ip Holdings Llc | Cable deployment apparatus, system, and methods for suspended load control equipment |
| US11618566B1 (en) | 2019-04-12 | 2023-04-04 | Vita Inclinata Technologies, Inc. | State information and telemetry for suspended load control equipment apparatus, system, and method |
| US11834305B1 (en) | 2019-04-12 | 2023-12-05 | Vita Inclinata Ip Holdings Llc | Apparatus, system, and method to control torque or lateral thrust applied to a load suspended on a suspension cable |
| US10838099B1 (en) * | 2019-05-14 | 2020-11-17 | Institute Of Geology And Geophysics, Chinese Academy Of Sciences | Multi-mode data observation method based on unmanned aerial vehicle formation for semi-airborne electromagnetic surveying |
| CN114423703A (en) | 2019-07-21 | 2022-04-29 | 维塔因克莱纳塔技术公司 | Elevator and deployable apparatus, devices, systems, and methods |
| US11620597B1 (en) | 2022-04-29 | 2023-04-04 | Vita Inclinata Technologies, Inc. | Machine learning real property object detection and analysis apparatus, system, and method |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| PL133163B1 (en) * | 1981-06-10 | 1985-05-31 | Instytut Gornictwa Naftowego Gaz | Method of and airborne system for directly exploring deposits of hydrocarbons |
| RU1770930C (en) * | 1990-06-29 | 1992-10-23 | Научно-производственное объединение "Взлет" | Device for towing magnetic field meter |
| CA2187952A1 (en) | 1996-10-16 | 1998-04-16 | Richard Stephen Taylor | Apparatus for airborne electromagnetic surveying |
| ZA9811489B (en) * | 1997-12-19 | 1999-06-18 | Anglo Amer Corp South Africa | Airborne electromagnetic system |
| RU2454684C2 (en) | 2002-11-20 | 2012-06-27 | Джеотек Эйрборн Лимитед | System for time domain airborne electromagnetic survey, comprising towed airborne electromagnetic survey apparatus |
| DE602005008938D1 (en) * | 2004-04-28 | 2008-09-25 | Anglo Operations Ltd | ELECTROMAGNETIC PROSPECTOR SYSTEM FOR HELICOPTERS |
-
2008
- 2008-02-25 US US12/036,657 patent/US7948237B2/en active Active
-
2009
- 2009-02-25 RU RU2010134804/28A patent/RU2494420C2/en active
- 2009-02-25 CN CN200980106631.9A patent/CN101981469B/en active Active
- 2009-02-25 DK DK09714643.5T patent/DK2247966T3/en active
- 2009-02-25 AU AU2009219062A patent/AU2009219062B2/en active Active
- 2009-02-25 CA CA2702346A patent/CA2702346C/en active Active
- 2009-02-25 EP EP09714643.5A patent/EP2247966B1/en active Active
- 2009-02-25 WO PCT/CA2009/000217 patent/WO2009105873A1/en active Application Filing
- 2009-02-25 BR BRPI0906004A patent/BRPI0906004A8/en not_active Application Discontinuation
-
2010
- 2010-08-19 ZA ZA2010/05931A patent/ZA201005931B/en unknown
-
2011
- 2011-05-23 US US13/113,582 patent/US8766640B2/en active Active
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106164706A (en) * | 2014-02-28 | 2016-11-23 | 艾克讯通讯有限公司 | The airborne platform including attitude updating device and the towing hitch assembly being associated for aircraft |
| CN105083554A (en) * | 2014-05-14 | 2015-11-25 | 空客直升机德国有限公司 | External load mass rope of a rotorcraft |
| US9845154B2 (en) | 2014-05-14 | 2017-12-19 | Airbus Helicopters Deutschland GmbH | External load mass rope of a rotorcraft |
| CN104443415A (en) * | 2014-11-27 | 2015-03-25 | 湖南航天机电设备与特种材料研究所 | Carrying structure for aviation transient electromagnetic coil |
| CN105824049A (en) * | 2016-03-21 | 2016-08-03 | 哈尔滨飞机工业集团有限责任公司 | Hanging-type helicopter time domain aeromagnetic detection pod |
| CN106199741A (en) * | 2016-07-04 | 2016-12-07 | 哈尔滨工业大学 | A kind of pod propulsion time domain aviation transient electromagnetic exploration system based on lightweight gas tube supporting construction |
| CN106226820A (en) * | 2016-07-04 | 2016-12-14 | 哈尔滨工业大学 | A kind of lightweight inflation ring supporting construction for pod propulsion time domain aviation transient electromagnetic exploration system |
| CN107102369A (en) * | 2017-06-05 | 2017-08-29 | 吉林大学 | Airborne low-temperature superconducting nuclear magnetic resonance shallow-layer oil seepage detection device and detection method |
| CN112068211A (en) * | 2020-07-30 | 2020-12-11 | 成都理工大学 | Half time domain electromagnetic prospecting system of aviation of unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| US7948237B2 (en) | 2011-05-24 |
| US8766640B2 (en) | 2014-07-01 |
| ZA201005931B (en) | 2011-10-26 |
| EP2247966A1 (en) | 2010-11-10 |
| WO2009105873A1 (en) | 2009-09-03 |
| US20110272522A1 (en) | 2011-11-10 |
| BRPI0906004A2 (en) | 2015-06-30 |
| EP2247966B1 (en) | 2017-06-21 |
| AU2009219062B2 (en) | 2013-01-10 |
| AU2009219062A1 (en) | 2009-09-03 |
| CN101981469B (en) | 2014-04-16 |
| BRPI0906004A8 (en) | 2018-01-02 |
| CA2702346C (en) | 2011-11-01 |
| RU2494420C2 (en) | 2013-09-27 |
| RU2010134804A (en) | 2012-04-10 |
| CA2702346A1 (en) | 2009-09-03 |
| EP2247966A4 (en) | 2011-04-06 |
| US20090212778A1 (en) | 2009-08-27 |
| DK2247966T3 (en) | 2017-09-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101981469B (en) | Airborne electromagnetic transmitter coil system | |
| CN102016644B (en) | Double-suspension receiver coil system and apparatus | |
| RU2454684C2 (en) | System for time domain airborne electromagnetic survey, comprising towed airborne electromagnetic survey apparatus | |
| AU2005238718B2 (en) | Helicopter electromagnetic prospecting system | |
| CN102770784B (en) | The towing assembly of geophysical exploration is carried out for Fixed Wing AirVehicle | |
| US9645274B2 (en) | Airborne electromagnetic system with rigid loop structure comprised of lightweight modular non-rotational frames | |
| US8674701B2 (en) | Airborne electromagnetic transmitter coil system | |
| AU2016231570B2 (en) | Airborne platform for aircraft, comprising attitude correcting means, and associated tow hitch assembly | |
| US11624852B2 (en) | Natural EM source airborne geophysical surveying system | |
| AU2014253658B2 (en) | Transmitter coil system for airborne surveys | |
| CN115097528A (en) | Aerial electromagnetic signal observation device and system carried by unmanned aerial vehicle | |
| CN210072087U (en) | Underwater electromagnetic detector capable of distinguishing directions | |
| AU2007202492B2 (en) | Airborne Electromagnetic Time Domain System, Computer Product and Method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170803 Address after: Ontario, Canada Patentee after: Jill Teco Ltd Address before: Babado J San Michael Patentee before: Geotech Ltd. |